Evaluation of discharge energy for separation flow control around NACA0015 airfoil controlled by nanosecond-pulse-driven plasma actuator

Atsushi Komuro, Keisuke Takashima, Kento Suzuki, Shoki Kanno, Sagar Bhandari, Taku Nonomura, Toshiro Kaneko, Akira Ando, Keisuke Asai

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Citations (Scopus)

Abstract

Energy efficiency of separated flow control by a nanosecond-pulse-driven plasma actuator (ns-DBDPA) was evaluated via wind tunnel experiments with a flow velocity of 40 m/s under atmospheric pressure. The dependence of the lift and drag coefficient on the different voltage amplitude shows that the optimal operating condition of the ns-DBDPA is estimated not by the sum of the discharge energy per unit time (discharge power) but by the discharge energy per single pulse. The results of the particle image velocimetry (PIV) show that the two vortices are shed by the pulse discharge from the leading edge of the airfoil where the ns-DBDPA is placed. Schlieren images show that the trajectories of the heated-zone produced by the discharge are equivalent to those of two vortices. These results indicate that the change in gas density caused by inputting the discharge energy to the air induces the formation of two vortices, thereby resulting in flow control.

Original languageEnglish
Title of host publicationAIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Edition210059
ISBN (Print)9781624105241
DOIs
Publication statusPublished - 2018 Jan 1
EventAIAA Aerospace Sciences Meeting, 2018 - Kissimmee, United States
Duration: 2018 Jan 82018 Jan 12

Publication series

NameAIAA Aerospace Sciences Meeting, 2018
Number210059

Other

OtherAIAA Aerospace Sciences Meeting, 2018
CountryUnited States
CityKissimmee
Period18/1/818/1/12

ASJC Scopus subject areas

  • Aerospace Engineering

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